The Effect of Nose Shape and Afterbody Length on the Normal Force and Neutral Point Location of Axisymmetric Bodies at Mach Numers from 0.08 to 4.50 PDF Download

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The Effect of Nose Shape and Afterbody Length on the Normal Force and Neutral Point Location of Axisymmetric Bodies at Mach Numers from 0.08 to 4.50

The Effect of Nose Shape and Afterbody Length on the Normal Force and Neutral Point Location of Axisymmetric Bodies at Mach Numers from 0.08 to 4.50 PDF Author: Donald Jacob Spring
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 92

Book Description

The Effect of Nose Shape and Afterbody Length on the Normal Force and Neutral Point Location of Axisymmetric Bodies at Mach Numers from 0.08 to 4.50

The Effect of Nose Shape and Afterbody Length on the Normal Force and Neutral Point Location of Axisymmetric Bodies at Mach Numers from 0.08 to 4.50 PDF Author: Donald Jacob Spring
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 92

Book Description

A Wind-tunnel Investigation of Effects of Noise Bluntness, Face Shape, and Afterbody Length on the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.98, and 3.90

A Wind-tunnel Investigation of Effects of Noise Bluntness, Face Shape, and Afterbody Length on the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.98, and 3.90 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 48

Book Description

Effects of Jet Billowing on Stability of Missile-type Bodies at Mach 3.85

Effects of Jet Billowing on Stability of Missile-type Bodies at Mach 3.85 PDF Author: Reino J. Salmi
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 22

Book Description

Summary of Static Stability and Drag Characteristics of Axisymmetric Low-drag Shapes for the Subsonic to Hypersonic Mach Number Range

Summary of Static Stability and Drag Characteristics of Axisymmetric Low-drag Shapes for the Subsonic to Hypersonic Mach Number Range PDF Author: Amado A. Trujillo
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 44

Book Description

A Wind-tunnel Investigation of the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.98, and 3.90 at Angles of Attack to 90 Deg

A Wind-tunnel Investigation of the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.98, and 3.90 at Angles of Attack to 90 Deg PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 40

Book Description

Some Effects of Nose Bluntness and Fineness Ration on the Static Longitudinal Aerodynamic Characteristics of Bodies of Revolution at Bussonic Speeds

Some Effects of Nose Bluntness and Fineness Ration on the Static Longitudinal Aerodynamic Characteristics of Bodies of Revolution at Bussonic Speeds PDF Author: William C. Hayes
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 70

Book Description

Effects of Body Shape on the Aerodynamics of a Body of Revolution at Mach Numbers from 1.6 to 4.6

Effects of Body Shape on the Aerodynamics of a Body of Revolution at Mach Numbers from 1.6 to 4.6 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26

Book Description

Aerodynamics of Tactical Weapons to Mach Number 8 and Angle of Attack 180°

Aerodynamics of Tactical Weapons to Mach Number 8 and Angle of Attack 180° PDF Author: Leroy Devan
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics).
Languages : en
Pages : 192

Book Description

The Effect of Cross-section Distribution on the Static Stability Characteristics of Axi-symmetric Bodies at Mach Numbers of 5.35 and 6.71

The Effect of Cross-section Distribution on the Static Stability Characteristics of Axi-symmetric Bodies at Mach Numbers of 5.35 and 6.71 PDF Author: J. F. Reilly
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 78

Book Description
An investigation was made at hypersonic Mach numbers to determine the effects of cross-section distribution on the static stability characteristics of bodies of revolution and to obtain the aerodynamic characteristics of these bodies. All of the bodies tested had the same length and all were circular in cross-section. The bodies tested were conic, bi-conic, and tri-conic. The tests were performed at Mach numbers of 5.35 and 6.71, and at unit Reynolds numbers from 1.5 x 100,000 to 3.2 x 100,000 per centimeter. The results indicate that under certain test conditions a body with a forecone followed by a frustum or frustum-flare combination exhibits, through the flow mechanism on the upper quarter of the body, an adverse center of pressure travel in the low angle of attack region (0 to 5 degrees). For a given moment reference point this yields both stable and unstable trim-points. (Author).

Stability Investigation of a Blunted Cone and a Blunted Ogive with a Flared Cylinder Afterbody at Mach Numbers from 0.30 to 2.85

Stability Investigation of a Blunted Cone and a Blunted Ogive with a Flared Cylinder Afterbody at Mach Numbers from 0.30 to 2.85 PDF Author: Lucille C. Coltrane
Publisher:
ISBN:
Category : Aircraft
Languages : en
Pages : 32

Book Description

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